R.M. Botez, A. Hiliuta, and L. Grigorie (Canada)
aerodynamics, simulation, aircraft model, aeroservoelasticity, aeroelasticity
An important aeroservoelasticity aspect is the analysis of interactions between rigid, elastic and control modes. We know that the rigid aerodynamic modes are not well calculated by use of finite element software for aeroelastic analysis such as Nastran [1], STARS [2], etc. For this reason, the flight dynamics of a rigid aircraft F/A-18 is validated by two different methods and the rigid and control modes interactions aerodynamic forces thus calculated replace the rigid and control modes interactions aerodynamic forces calculated with finite element software. Results obtained with these two methods (numerical and analytical) are identical, and the aerodynamic model of the F/A-18 is validated by use of Matlab software and Simulink toolbox. The first method calculates analytically the aerodynamic rigid and control forces in the inertial system of coordinates from stability and control derivatives in the wind system of coordinates. The second method, here presented, is a simulation and numerical method by which the aerodynamic forces are also calculated by use of dlinmod Matlab command in Simulink.
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